US3666043A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Air divider ring structure for jet engine inlet air duct
Assignee: Rohr Inc
•
Filing: 1970-11-12
•
Granted: 1972-05-30
•
Expires: 1990-11-12
Abstract
Abstract One or more inlet air dividing, sound absorptive rings are supported co-axially within the inlet duct of a jet engine nacelle on a plurality of radially inwardly extending, streamlined struts. In one form of the invention, these struts are telescopically extensible and retractable to move the rings from deployed position concentrically in the air duct to stowed condition within the cowl defining the air duct. In the other forms of the invention each sound absorptive ring comprises a plurality of arcuate acoustical honeycomb panel sections releasably connected at their lateral edges by piano hinge type connectors to narrow longerons supported by said struts, the panel sections and the longerons comprising complementary segments of each sound absorptive ring.
Inventors
- 👤 Rodney Eschenburg
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 11:23
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/04; F02C7/045
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
149 words
Sound suppression mechanism for an aircraft jet engine having a cowl with an annular inner wall defining an air inlet duct coaxially of and forwardly of the engine, said mechanism comprising: a plurality of panel receiving pockets formed in symmetrically, circumferentially spaced relation in the cowl inner wall, a set of splitter ring panels of a size and shape to fit, in relatively superposed, stowed relation, into each pocket, extensible strut means mounted in each pocket and operatively connected to the panels in each pocket, each strut means being extensible from stowed position, with the panels of its respective set stowed in their respective pocket, to extended position with corresponding panels of each set deployed at equally spaced intervals from the cowling, and co-axially of the air inlet duct, whereby the corresponding panels of each set define an annulus co-axial with each other and with the air inlet duct.
Claim 2
Dependent Claim
149 words
Sound suppression mechanism for an aircraft jet engine having a cowl with an annular inner wall defining an air inlet duct coaxially of and forwardly of the engine, said mechanism comprising: a plurality of panel receiving pockets formed in symmetrically, circumferentially spaced relation in the cowl inner wall, a set of splitter ring panels of a size and shape to fit, in relatively superposed, stowed relation, into each pocket, extensible strut means mounted in each pocket and operatively connected to the panels in each pocket, each strut means being extensible from stowed position, with the panels of its respective set stowed in their respective pocket, to extended position with corresponding panels of each set deployed at equally spaced intervals from the cowling, and co-axially of the air inlet duct, whereby the corresponding panels of each set define an annulus co-axial with each other and with the air inlet duct.
Claim 3
Dependent Claim
45 words
Sound suppression mechanism as defined in claim 1 wherein the innermost panel of each set is of a size and shape to have lateral, edgewise, contacting relation with the lateral edges of the innermost panels on both sides thereof with the panels in deployed position.
Claim 4
Dependent Claim
66 words
Sound suppression mechanism as claimed in claim 1 wherein the panels of each set comprise at least an inner splitter ring panel shaped to fit into and to close the opening into its respective pocket with the panels in their stowed position, and an outer closure panel shaped to fit into and to close the opening into the pocket with the panels in their deployed position.
Claim 5
Dependent Claim
43 words
Sound suppression mechanism as defined in claim 3 wherein at least one splitter ring panel is provided intermediately of each inner panel and its respective outer closure panel, and the outer closure panel is fixedly connected in spaced relation to such intermediate panel.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-05-30 | 1975-11-29 | 1976-05-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-05-30 | 1979-11-29 | 1980-05-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-05-30 | 1983-11-29 | 1984-05-30 | $7700.00 | Window Closed / Lapsed |